Rotatable structures support method and means

ABSTRACT

A cantilever arrangement for independently suspending two spaced guide assemblies for launching missiles is provided. The spaced assemblies are coupled one on each end of a cylindrical section to elevation bearings and are interconnected by external tubular trusses for transmitting elevation drive from one assembly to the other.

METHOD AND MEANS Carroll D. Phillips, Weston, Mass.

The United States of America as represented by the Secretary of the Navy, Washington, DC

Filed: Nov. 1, 1973 Appl. No.: 412,371

Inventor:

Assignee:

US. Cl. 8911.815; 89/37 R Int. Cl F4lf 3/04 Field of Search.......... 89/37 R, 37.5 R, 37.5 A,

89/375 E, 41 R, 1.815, L8l6, 1.8

Sanders 89/375 A United States Patent [1 1 3,892,162 Phillips [4 1 July 1, 1975 [54] ROTATABLE STRUCTURES SUPPORT 2,364,425 l2/l944 Corte 89/375 A X 2,399,200 4/l946 Brown 89/375 A X Primary Examiner-Robert F. Stahl Attorney, Agent, or FirmR. S. Sciascia; C. E. Vautrain, Jr.

[57] ABSTRACT A cantilever arrangement for independently suspending two spaced guide assemblies for launching missiles is provided. The spaced assemblies are coupled one on each end of a cylindrical section to elevation bearings and are interconnected by external tubular trusses for transmitting elevation drive from one assembly to the other.

2 Claims, 4 Drawing Figures ROTATABLE STRUCTURES SUPPORT METHOD AND MEANS The present invention concerns drive mechanisms and, more particularly, a missile launch system for coupling together balanced sets of launch guide cells without requiring a centrally connected torque tube.

The conventional way of coupling two balanced launch assemblies for launching a plurality of missiles is to mount the two assemblies on opposite ends of an interconnecting torque tube. Elevation and train forces are applied to the torque tube and carried by the tube to the remotely positioned launch assemblies. This arrangement is undesirable since it requires a heavy torque tube which, in turn, requires bearings, housings, etc. that occupy and render unusable substantially all of the area between the launch assemblies. This torque tube and its bearing surfaces, being positioned directly between the launch assemblies, necessitates that the cabling and electronics associated with the assemblies be positioned at some remote location which positioning is undesirable since it occupies additional space and presents additional opportunity for damage to and malfunctioning of the equipment. The present invention avoids the foregoing disadvantages by providing a working area between launch assemblies in which may be accomodated the electronics, cabling and motoring necessary to control and operate the launch assemblies.

According to the present invention, the elevation drive system of a NATO Seasparrow launcher which includes a four mesh, spur involute gear drive mechanism, cabling and electronics is positioned in and only partially occupies the space between the launchers twin launch guide assemblies. The launch guide assemblies are supported at the ends of a central structural cylinder by independent x-roller bearings which are capable of taking loads in all directions including overhung cantilever moments. The guide assemblies are interconnected at their adjacent extremities by at least three truss members that transmit elevation drive eccentrically from one guide into the other, and generally synchronize boresight between the two guide assemblies.

Accordingly, it is an object of the present invention to provide means for supporting twin rotatable assemblies wherein the support means afi'ords usable space for equipment, controls, etc.

Another object of this invention is to provide means for supporting balanced pivotable and rotatable objects by a central section which is capable of taking loads in all directions.

A further object of this invention is to provide means for supporting a pair of twin rotatable and trainable assemblies in an arrangement which permits lateral cantilever support of the assemblies.

Other objects, advantages and novel features of the invention will become apparent from the following detailed description thereof when considered in conjunction with the accompanying drawings in which like numerals represent like parts throughout and wherein:

FIG. I is a perspective view of a missile launcher showing a preferred embodiment of the invention in an assembled launcher;

FIG. 2 is a perspective view of the launcher of FIG. I and its supporting structure showing details of the launch assemblies and the cylindrical section supporting them;

FIG. 3 is a perspective view of the cylindrical support of FIGS. 1 and 2 before assembly; and

FIG. 4 is a perspective view of the end of the cylindrical support of FIG. 3 in partially assembled condition.

Referring to FIG. 1, a NATO Seasparrow launcher 11 is shown which includes a pair of twin launch assemblies l4 and 15 and a pedestal l7 and cylindrical support 18 for supporting and controlling the movement of the launch assemblies. In FIG. 2 launch assemblies 14 and 15 and cylindrical support 18 are shown in a cutaway view which illustrates the controls, cables, equipment, etc. which may be contained in support 18. Some major items are train drive motors l9 and an elevation cable loop 20.

FIG. 3 shows cylindrical support 18 before being mounted on its pedestal and before having the launch assemblies mounted on and in it. Cylinder 18 has secured to either of its ends circumferential flanges 21 and 22 to which cross-roller type bearings 30 shown in FIG. 4 are secured. A gear box 35 containing an elevation gear reducer and a motor 36 is secured to support 18. The elevation gear reducer includes the spur gears and other components of a connventional four mesh spur involute gear drive system. The output pinion of the system is protected by a housing 37 and meshes with gear teeth 38 to drive launch assembly 15 in elevation. Launch assembly 14 is driven by launch assembly 15 through a plurality of three truss members 39 in FIGS. 1 and 2. An opening 40 in an end plate 41 provides a passage for cables which connect components of launch assembly 15 to the launcher controls. A similar plate 43 in FIG. 3 has openings 44 and 45 for passage of cables of launch assembly 14. Cylindrical support 18 is mounted on pedestal 17 for train in the same manner and using the same bearing arrangement, not shown, as elevation bearing 30.

Bearing 30 is a conventional diamond shaped crossroller type which provides large load capacity for resisting shock loads. low friction, high stiffness, and the capability of carrying vertical, shear and moment type loads.

Although some mechanical details have been ommited, those details essential to an understanding of the invention have been presented. The cross-roller type bearing used has its external race bolted to the fixed pedestal structure 17 for train and to the cylindrical support 18 for elevation. The internal races, or rotating members of these bearings are fixed to the launch guide assemblies and the cylindrical section and are driven by the output pinions of the respective gear boxes. Two bearings are used. one each for rotation of launch assemblies 14 and 15 about the elevation or pitch axis. Thus. each launch assembly is mounted to its own elevation bearing on each side of the central cylindrical support for cantilever support and both launch assemblies are couplied together by the central support for rotation about the train or yaw axis. Since only one launch assembly is driven by the drive gear box 35 pinion, the two launch assemblies are interconnected by truss assembly 39 which preferably is formed of tubular structural members capable of transmitting elevation drive torque from launch assembly 15 to launch assembly 14.

There is thus provided an improved means for mounting a pair of balanced rotatable structures on a central housing which is disposed between the structures and from which the structures are independently suspended. The central area of the housing is free of mechanical components associated with the elevation or train motion of the rotatable structures. The area between the structures can now accomodate electronic components, a substantial number of cables, axis drive motors, and drive gear assemblies, etc. which in a conventional mounting would necessitate additional remote housing. Preferably only one structure is driven and the drive means occupies only a small portion of the space in the central housing. Both structures are supported in identical cantilever fashion on respective ends of the housing. The support means is in each case a diamond shaped cross-roller type bearing which performs the dual function of structural support and bearing support to accomodate rotary motion. This type of cross-roller bearing is preferred because of its high load capacity, resistance to shock, and stiffness. The diameter of the cross-roller bearings in combination with the interconnecting truss structure is of such magnitude that superior precision in coupling and in movement are achieved over the conventional centrally positioned torque tube member. A substantial weight may be sus pended on each side of the central housing in the manner described and driven smoothly in elevation. The central housing also may be mounted on a similarly sized pedestal for rotation in train on a similar crossroller type bearing upon which the central housing is mounted and driven in a similar smanner.

Obviously many modifications and variations of the present invention are possible in the light of the above teachings. For example, the cross-roller bearing may be replaced by similar angle contact ball bearings which would perform the same function.

What is claimed is:

l. A system for independently and rotatably suspending two spaced missile launch assemblies comprising:

a central structural cylindrical housing disposed between said assemblies with the longitudinal axis of said housing collinear with common transverse axes of said assemblies;

a circumferential flange secured to each end of said housing adjacent each assembly for providing cantilevered, rotatable support of said assemblies thereon; a motor in said housing for driving at least one of said assemblies about its said common transverse axis, said one assembly driven internally with respect to said housing so that said motor may be coupled directly to said means for providing support of said assemblies,

said housing providing internal space for cables and electronic components and other equipment associated with the control of said motor and said assemblies;

means external to said housing coupling the other of said assemblies to said driven assembly so that both assemblies will rotate in unison; and

a pedestal supporting said housing and means in said pedestal connected to said housing for rotating said housing about an axis orthogonal with respect to said collinear axis,

whereby assemblies such as twin missile launch guide assemblies may be substantially powered and controlled by internally contained equipment to provide azimuth and elevation control of said assemblies and launch control of the missiles in said assemblies.

2. The system defined in claim 1 and further including cross-roller bearing means having a race which is secured to said housing,

said assemblies balanced and mounted on and supported by said race;

a drive motor and a gear drive system connected thereto positioned in said pedestal for rotating said housing; and

cross-roller bearing means secured to said pedestal and a bearing ring secured to said housing and rotatably coupled to said pedestal mounted crossroller bearing means for supporting said central housing. 

1. A system for independently and rotatably suspending two spaced missile launch assemblies comprising: a central structural cylindrical housing disposed between said assemblies with the longitudinal axis of said housing collinear with common transverse axes of said assemblies; a circumferential flange secured to each end of said housing adjacent each assembly for providing cantilevered, rotatable support of said assemblies thereon; a motor in said housing for driving at least one of said assemblies about its said common transverse axis, said one assembly driven internally with respect to said housing so that said motor may be coupled directly to said means for providing support of said assemblies, said housing providing internal space for cables and electronic components and other equipment associated with the control of said motor and said assemblies; means external to said housing coupling the other of said assemblies to said driven assembly so that both assemblies will rotate in unison; and a pedestal supporting said housing and means in said pedestal connected to said housing for rotating said housing about an axis orthogonal with respect to said collinear axis, whereby assemblies such as twin missile launch guide assemblies may be substantially powered and controlled by internally contained equipment to provide azimuth and elevation control of said assemblies and launch control of the missiles in said assemblies.
 2. The system defined in claim 1 and further including cross-roller bearing means having a race which is secured to said housing, said assemblies balanced and mounted on and supported by said race; a drive motor and a gear drive system connected thereto positioned in said pedestal for rotating said housing; and cross-roller bearing means secured to said pedestal and a bearing ring secured to said housing and rotatably coupled to said pedestal mounted cross-roller bearing means for supporting said central housing. 